Method of manufacturing a mistuned rotor
A method includes: obtaining a rotor having a hub and a plurality of blades protruding from the hub, the plurality of blades including first blades and second blades disposed in alternation around a central axis of the rotor, natural vibration frequencies of the first blades different from natural vibration frequencies of the second blades; determining that a difference between a first natural vibration frequency of a first blade of the first blades and a second natural vibration frequency of a second blade of the second blades is below a threshold; and modifying a shape of the first blade until the difference between the first natural vibration frequency and the second natural vibration frequency is at or above the threshold.
1. A method comprising:
manufacturing a rotor having a hub and a plurality of blades protruding from the hub, the plurality of blades including first blades and second blades disposed in alternation around a central axis of the rotor to form pairs, a pair of the pairs including a first blade of the first blades disposed adjacent to a second blade of the second blades, the first blades having a natural vibration frequency differing from a natural vibration frequency of the second blades by a frequency difference for mistuning the rotor, the rotor being an integrally bladed rotor such that the plurality of blades and the hub are parts of a monolithic body of the rotor;
performing an analysis on the monolithic body of the rotor with the plurality of blades and the hub to obtain actual frequency differences for each of the pairs;
determining that an actual frequency difference corresponding to the pair of the pairs is below a minimum threshold; and
re-working the integrally bladed rotor by modifying a shape of one or more of the first blade and the second blade of the pair such that a modified frequency difference between natural vibration frequencies of the first blade and the second blade of the pair is at or above the threshold;
wherein the modifying of the shape of the first blade of the pair includes modifying the shape of the first blade within a zone on an aerodynamic surface of the first blade by creating a recessed area within the zone;
wherein the creating of the recessed area includes increasing a depth of the recessed area from a perimeter of the zone toward a location within the zone, a depth of the recessed area being maximal at the location; and
wherein a chordwise rate of variation of the depth is greater from the leading edge to the location of greatest depth than from the location to the trailing edge.
2. The method of claim 1 , comprising identifying a zone on the first blade of the pair, the modifying of the shape of the first blade of the pair including modifying the shape of the first blade by modifying the shape of the first blade within the zone.
3. The method of claim 2 , wherein the modifying of the shape of the first blade of the pair within the zone includes removing matter from the first blade within the zone.
4. The method of claim 1 , wherein the modifying of the shape of the first blade of the pair includes modifying a shape of a pressure side of the first blade.
5. The method of claim 1 , wherein the modifying of the shape of the first blade of the pair within the zone includes modifying the shape of the first blade within the zone located radially outwardly of a mid-span line of the first blade.
6. The method of claim 1 , wherein the modifying of the shape of the first blade of the pair within the zone includes modifying the shape of the first blade within the zone being offset from a leading edge of the first blade.
7. The method of claim 6 , wherein the modifying of the shape of the first blade of the pair within the zone includes modifying the shape of the first blade within the zone being offset form a trailing edge of the first blade.
8. The method of claim 1 , wherein the location is offset from a center of the zone.
9. The method of claim 1 , comprising compensating for a rotational imbalance created by the modifying of the shape of the first blade of the pair.
10. The method of claim 9 , wherein the compensating for the rotational imbalance includes securing counterweights on the rotor.
11. A method comprising:
manufacturing a rotor having a hub and a plurality of blades protruding from the hub, the plurality of blades including first blades and second blades disposed in alternation around a central axis of the rotor to form pairs, a pair of the pairs including a first blade of the first blades disposed adjacent to a second blade of the second blades, the first blades having a natural vibration frequency differing from a natural vibration frequency of the second blades by a frequency difference for mistuning the rotor, the rotor being an integrally bladed rotor such that the plurality of blades and the hub are parts of a monolithic body of the rotor;
performing an analysis on the monolithic body of the rotor with the plurality of blades and the hub to obtain actual frequency differences for each of the pairs;
determining that an actual frequency difference corresponding to the pair of the pairs is below a minimum threshold; and
re-working the integrally bladed rotor by modifying a shape of one or more of the first blade and the second blade of the pair such that a modified frequency difference between natural vibration frequencies of the first blade and the second blade of the pair is at or above the threshold;
wherein the modifying of the shape of the first blade of the pair includes modifying the shape of the first blade within a zone on an aerodynamic surface of the first blade by creating a recessed area within the zone;
wherein the creating of the recessed area includes increasing a depth of the recessed area from a perimeter of the zone toward a location within the zone, a depth of the recessed area being maximal at the location; and
wherein a spanwise rate of variation of the depth is greater from a base of the first blade to the location of greatest depth than from the location to a tip of the first blade.
12. The method of claim 11 , comprising identifying a zone on the first blade of the pair, the modifying of the shape of the first blade of the pair including modifying the shape of the first blade by modifying the shape of the first blade within the zone.
13. The method of claim 12 , wherein the modifying of the shape of the first blade of the pair within the zone includes removing matter from the first blade within the zone.
14. The method of claim 11 , wherein the modifying of the shape of the first blade of the pair includes modifying a shape of a pressure side of the first blade.
15. The method of claim 11 , wherein the modifying of the shape of the first blade of the pair within the zone includes modifying the shape of the first blade within the zone located radially outwardly of a mid-span line of the first blade.
16. The method of claim 11 , wherein the modifying of the shape of the first blade of the pair within the zone includes modifying the shape of the first blade within the zone being offset from a leading edge of the first blade.
17. The method of claim 16 , wherein the modifying of the shape of the first blade of the pair within the zone includes modifying the shape of the first blade within the zone being offset form a trailing edge of the first blade.
18. The method of claim 11 , wherein the location is offset from a center of the zone.
19. The method of claim 11 , comprising compensating for a rotational imbalance created by the modifying of the shape of the first blade of the pair.
20. The method of claim 19 , wherein the compensating for the rotational imbalance includes securing counterweights on the rotor.